Helicopter seat system capable of automatically changing load and absorbing energy

Abstract

The utility model provides a helicopter seat system capable of automatically changing load and absorbing energy, which comprises a frame, a bulletproof armored seat basin, an electronic controller, an adjusting and locking mechanism, a guide rail, an electric push rod and an automatic load-changing and energy-absorbing device, the guide rail is fixed on a cabin floor, the frame is arranged on the guide rail, and a round hole is arranged on the upper surface of the guide rail. The seat system can be controlled to slide back and forth and adjust a locking mechanism to slide on a guide rail and to be locked at a round hole of the guide rail, a bulletproof armored seat basin is installed on a movable seat leg of the frame and is fixed through a bolt, and the upper end of an automatic variable load energy absorption device is connected with an energy absorber connector of the frame through a bolt. The lower end of the automatic variable-load energy-absorbing device is connected with a lower connector installed on the bulletproof armored chair basin through a bolt, the electronic controller is installed on the bulletproof armored chair basin and connected with the automatic variable-load energy-absorbing device through a cable to achieve control, and the electric push rod is installed between an upper cross rod and a lower cross rod of the frame. The adjusting locking mechanism is provided with a handle and a locking mechanism which enable the adjusting locking mechanism to slide back and forth.

Description

Technical Field

[0001] The utility model relates to a seat technology for a helicopter or other aircraft, in particular to a helicopter seat system capable of automatically changing load and absorbing energy. Background Art

[0002] Helicopters, especially armed helicopters, have low flight altitudes and short reaction times for the control actions chosen by pilots before abnormal landing, so they are prone to falling and being damaged. Therefore, they must be designed to resist crashes. Helicopter anti-crash is mainly achieved through crash-adaptive design of landing gear, fuselage, seats and other components, such as energy-absorbing landing gear, crash-adaptive nose and fuselage structure, crash-resistant seats, crash-adaptive fuel tanks, etc. Crash-resistant seats mainly use energy-absorbing devices to maintain the integrity of the seat structure and limit the load transmitted from the fuselage to the pilot, thereby reducing the casualties of pilots in crash-survivable accidents. Energy-absorbing devices can be divided into fixed-load energy-absorbing devices and variable-load energy-absorbing devices. Fixed-load energy-absorbing devices can only provide the best protection for pilots of the 50th percentile weight; for heavy pilots, the energy-absorbing working load is set too small and there is a potential risk of secondary collision between the seat and the cabin floor; while light pilots may be injured by large overload shocks due to excessive energy-absorbing working loads.

[0003] The prior art discloses a helicopter crash-resistant seat with an inverted bow energy-absorbing structure, which absorbs crash energy through an inverted bow structure arranged at the bottom of the seat pan. The structure has the defects of insufficient crash energy absorption, the seat height cannot be adjusted to meet the eye position requirements of pilots of different percentiles, and the fixed load energy-absorbing device cannot adjust the energy-absorbing working load according to the weight of the pilot.

[0004] The prior art discloses an expanded tube type fixed load energy absorbing device, which absorbs crash energy by expanding the inner diameter of a thin-walled tube. This structure has the defects of uneven impact overload and the device being unable to adjust the energy absorbing working load according to the weight of the pilot.

[0005] The prior art also discloses an airbag type crash-resistant seat. Although the airbag realizes energy absorption and has the characteristic of all-round protection for personnel, it has defects such as complex structure, large size and heavy weight.

[0006] To sum up, the currently used helicopter crash-resistant seats adopt fixed load energy absorption devices and cannot adjust the energy absorption working load according to the weight of the pilot; they do not have the problem of bulletproof capability; they use springs to provide power, and the pure mechanical lifting adjustment and locking method is time-consuming and labor-intensive to adjust, and cannot be adjusted and locked steplessly, resulting in poor human-machine efficiency, and incomplete protection for helicopter crew members in complex battlefield environments, and do not take into account life-saving needs such as variable load energy absorption buffering and bulletproofing. Utility Model Content

[0007] The purpose of the utility model is: the utility model provides a helicopter seat system that can automatically change the load and absorb energy, can adjust its energy absorption working load according to the weight of the pilot, can provide equivalent protection for pilots of different percentile weights, and ensure that the overload borne by the pilot's lumbar spine does not exceed the tolerance limit of the human body.

[0008] The technical scheme of the utility model is: a helicopter seat system capable of automatically changing load and absorbing energy, comprising a frame, a bulletproof armored seat basin, an electronic controller, an adjustment locking mechanism, a guide rail, an electric push rod and an automatic variable load and energy absorbing device, the guide rail being fixed on the cabin floor, the frame being mounted on the guide rail, the upper surface of the guide rail being provided with a circular hole, the seat system being operable to slide forward and backward and the adjustment locking mechanism being slid on the guide rail and locked at the circular hole thereof, the bulletproof armored seat basin being mounted on the movable chair legs of the frame and being fixed by bolts, the upper end of the automatic variable load and energy absorbing device being connected to the energy absorber connecting joint of the frame by bolts, and the lower end thereof being connected to the lower joint mounted on the bulletproof armored seat basin by bolts, the electronic controller being mounted on the bulletproof armored seat basin, being connected to the automatic variable load and energy absorbing device by a cable and realizing control, the electric push rod being mounted between the upper cross bar and the lower cross bar of the frame, the adjustment locking mechanism being provided with a handle for making it slide forward and backward and a locking mechanism, the forward and backward sliding handle being mounted below the bulletproof armored seat basin, and the locking mechanism being mounted at the bottom of the main chair legs of the frame. The seat system includes at least one electric push rod for guiding at least one armored seat basin to move up and down to adjust the seat height. The electric push rod is a straight rod type, which can be extended and retracted to achieve stepless adjustment and self-locking travel.

[0009] In the above scheme, the seat system also includes a five-point safety belt, which includes an inertia reel and a control handle, wherein the inertia reel is installed on the back of the bulletproof armored seat basin, and the control handle is installed on the left front side of the bulletproof armored seat basin.

[0010] In the above scheme, the seat system also includes a headrest, a back pad, an electric push rod lumbar pad and a seat cushion. The headrest, the back pad, the electric push rod lumbar pad and the seat cushion are arranged and fixed at corresponding positions when the occupant is sitting. The seat cushion is made of a foamed part made of a double-layer material of polyurethane foam and flame-retardant low-resilience polyethylene foam. The headrest (4), the back pad and the electric push rod lumbar pad are made of a foamed part made of polyurethane foam material. The back pad is designed to be an "S" shape with two points of support for the shoulder and waist. The seat cushion is tilted up to provide appropriate support for the pilot's thighs. The angle between the seat surface and the horizontal plane is 7°, and the angle between the back of the back pad and the seat surface of the seat cushion is 113°, so as to ensure the pilot's riding comfort.

[0011] In the above scheme, the seat system includes at least one frame, which is fixed to the floor through a guide rail to carry the armored seat basin. Among them: the movable chair legs in the frame can move up and down relative to the main chair legs through bushings to adjust the seat height; the upper sliding sleeve assembly and the lower sliding sleeve assembly in the frame can move up and down on the movable chair legs, and an effective buffer space is reserved for carrying the armored seat basin and the pilot downward for buffering when the energy absorption device is working; the relative movement position of the frame is coated with solid dry film lubricant; the guide rail is connected to the floor, and the guide rail is in the form of an I-beam with a round hole on the upper surface; the contact position between the front and rear sliding block assemblies and the upper surface of the guide rail is provided with a long polytetrafluoroethylene gasket, which has good sliding performance.

[0012] In the above scheme, the contact position between the upper sliding sleeve assembly and the movable chair leg surface is respectively provided with a polytetrafluoroethylene gasket and a rolling bearing, which has good sliding performance. The contact position between the lower sliding sleeve assembly and the movable chair leg surface is provided with a rolling bearing, which has good sliding performance. The distance between the main chair legs can be adjusted according to the requirements of the floor interface of different models of aircraft.

[0013] The automatic variable load energy absorption device has at least one, which first measures the effective weight information of the pilot sitting on the seat through a weight sensor and sends data. After receiving the effective weight data, the electronic controller analyzes and calculates and sends the position information of the worm gear adjustment ring corresponding to the weight of the occupant to the servo motor. The servo motor receives the command and drives the worm gear to drive the worm gear adjustment ring to rotate. As the worm gear adjustment ring rotates, the steel ball either moves toward the center of the rolling tube or moves away from its direction, so that the protrusion of the steel ball in the spherical groove of the rolling tube can be adjusted. The size of the protrusion of the steel ball determines the size of the energy absorption work load. During the adjustment process, the rotary transformer monitors the angle position information in real time. When the specified position is reached, the servo motor stops working, and then the energy absorption work load is adjusted to the optimal working state corresponding to the effective weight of the pilot. Once an emergency landing accident occurs, the rolling tube and the roll tube in the energy absorption device undergo plastic deformation to absorb energy. At this time, the energy absorption device extends and ensures that the movable part of the human chair moves downward at 14.5g, preventing the pilot's lumbar spine from being overloaded and causing damage.

[0014] The bulletproof armored seat basin and side armor both adopt a bulletproof structure in which a bulletproof ceramic panel is pasted on the outside of a carbon fiber load-bearing member and an ultra-high molecular weight polyethylene plate is pasted on the inside. Crack-stop cloth is wrapped and pasted on the outside of the bulletproof ceramic panel, and all armor edges are covered with edge strips to protect the pilot from being cut by the ceramic edges.

[0015] In the above scheme, the seat system includes at least one electric push rod for guiding at least one armored seat basin to move up and down to adjust the seat height. The electric push rod is a straight rod type, which can be extended and retracted to achieve stepless adjustment and the stroke can be self-locking.

[0016] The utility model has the advantages and beneficial effects: the seat system provided by the utility model has the ability to resist crashes and absorb energy. When the helicopter crashes and the overload reaches a certain threshold, the thin-walled rolled tube and the flip tube of the energy absorbing device will undergo plastic deformation to attenuate the impact energy. The working load value of the energy absorber is designed according to the human tolerance limit, and the automatic matching with the pilot's weight is achieved through electronic control to avoid the possibility of human operation errors, which can meet the safety requirements of protecting pilots of different percentiles. The seat system has bulletproof ability and can resist the attack of 12.7 mm armor-piercing incendiary bombs. The seat system is equipped with a five-point safety belt, which can provide restraint for personnel during normal riding or falling to the ground, and avoid the collision between the upper torso of the personnel and the equipment in the cabin. The seat system is equipped with a foam pad to ensure the comfort of the personnel. The seat system can be electrically raised and lowered to ensure the eye position requirements of the pilot; the seat system can be slid forward and backward on the guide rail fixed to the floor to ensure that the rudder position of pilots of different heights and body shapes is always kept in a suitable state when driving a helicopter, and the joystick can be easily operated. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The following figure is a diagram of an embodiment of the utility model:

[0018] Figure 1 It is a front view schematic diagram of the overall structure of the seat system of the utility model;

[0019] Figure 2 It is a schematic diagram of the overall structure of the seat system of the utility model from the back;

[0020] Figure 3 It is a structural schematic diagram of the automatic variable load energy absorption device of the utility model;

[0021] Figure 4 This utility model Figure 3 A-A structural diagram;

[0022] Figure 5 This utility model Figure 4 Enlarged view of middle C;

[0023] Figure 6 This utility model Figure 5 Schematic diagram of the B-B structure;

[0024] Figure 7 This is a schematic diagram of the structure of the rolling tube of the utility model;

[0025] Figure 8 This is a schematic diagram of the roll-up tube structure of the utility model;

[0026] Fig. 9 This is a schematic diagram of the structure of the worm gear adjustment ring of the utility model

[0027] Fig.10 This is a schematic diagram of the structure of the automatic variable load energy absorption device of the utility model after starting to work;

[0028] Fig.11 This is the appearance diagram of the electronic controller of the automatic variable load energy absorption device of the utility model;

[0029] Fig.12 This is a functional block diagram of the electronic controller of the automatic variable load energy absorption device of the utility model;

[0030] Fig.13 -16 is a schematic diagram of the structure of the framework of the utility model;

[0031] Fig.17 -18 is a schematic diagram of the structure of the armored chair basin of the utility model;

[0032] Fig.19 This is a schematic diagram of the structure of the front and rear sliding adjustment handle of the utility model;

[0033] Fig. 20 It is a schematic diagram of the front and rear sliding adjustment locking mechanism of the utility model.

[0034] In the figure: 1-frame, 2-bulletproof armored seat basin, 3-five-point safety belt, 4-headrest, 5-back cushion, 6-lumbar cushion, 7-seat cushion, 8-electronic controller, 9-adjustment locking mechanism, 10-guide rail, 11-electric push rod, 12-automatic variable load energy absorption device, 13-lower joint, 14-pressure nest, 201-rolling tube, 202-turning tube, 203-support tube, 204-connecting sleeve, 205-steel ball, 206-single ear joint, 207-support, 208-pull rod, 209 - pull head, 210 - bracket, 211 - steel ball fixed outer cylinder, 212 - joint, 213 - double ear joint, 214 - worm gear adjustment ring, 215 - worm, 216 - limit screw, 217 - servo motor, 218 - weight sensor, 219 - rotary transformer, 220 - chassis, 221 - transmission shaft, 222 - arc groove, 223 - worm gear, 224 - fixed end, 301 - main chair leg, 302 - movable chair leg, 303 - bushing, 304 - upper cross bar , 305 - lower cross bar, 306 - connecting joint, 307 - push rod connecting joint, 308 - upper sliding sleeve assembly, 309 - lower sliding sleeve assembly, 310 - front and rear sliding block assembly, 311 - long gasket, 312 - gasket, 313 - bearing hoop, 314 - bearing retaining ring, 315 - bearing, 316 - upper slider, 317 - lower slider, 318 - limit plate, 401 - left armor, 402 - right armor, 403 - armored chair basin, 404 - left bow, 405 - right Bow-shaped part, 501-mounting seat, 502-handle rotating connecting rod, 503-steel bushing, 504-torsion spring, 505-handle rod, 506-handle cover, 507-adjusting screw, 508-steel cable assembly, 601-front and rear sliding locking pin, 602-sleeve, 603-spring, 604-thin nut, 801-energy absorption device control button, 802-power light, 803-status indicator light, 804-seat height adjustment button, 805-connector interface, 806-display screen. DETAILED DESCRIPTION

[0035] The present invention is further described in detail below through specific implementation modes:

[0036] like Figure 1As shown in Figure 2, the seat system of the utility model includes a frame 1, a bulletproof armored seat base 2, a five-point safety belt 3, a headrest 4, a back cushion 5, an electric push rod waist cushion 6, a seat cushion 7, an electronic controller 8, an adjustment locking mechanism 9, a guide rail 10, an electric push rod 11, an automatic variable load energy absorption device 12, etc. The guide rail 10 is fixed on the cabin floor, the frame 1 is installed on the guide rail 10, and the upper surface of the guide rail 10 has a circular hole. The seat system can manipulate the adjustment locking mechanism 9 to slide on the guide rail 10 and lock at its circular hole. The bulletproof armored seat base 2 is installed on the movable chair leg of the frame 1 and fixed by bolts. The upper end of the automatic variable load energy absorption device 12 is connected to the energy absorber connection joint of the frame 1 by bolts, and the lower end thereof is connected to the lower joint 13 installed on the bulletproof armored seat base 2 by bolts. The electronic controller 8 is installed on the bulletproof armored seat base 2, and it is connected to the automatic variable load energy absorption device 12 by a cable to realize control. The five-point safety belt 3 is installed on the bulletproof armored seat basin 2, and its inertia reel is installed on the back of the bulletproof armored seat basin 2, and its control handle is installed on the left front side of the bulletproof armored seat basin 2. The electric push rod 11 is installed between the upper crossbar and the lower crossbar of the frame 1. The front and rear sliding handles of the adjustment locking mechanism 9 are installed below the bulletproof armored seat basin 2, and its locking mechanism is installed at the bottom of the main chair leg of the frame 1. The five-point safety belt can effectively restrain the pilot in an emergency landing state and prevent dynamic diving. Its inertia reel has automatic locking and manual locking functions.

[0037] The seat cushion is made of a double-layer material of polyurethane foam and flame-retardant low-rebound polyethylene foam, and the back pad, headrest and waist pad are made of polyurethane foam. The seat pad is designed according to the principles of ergonomics, and fully considers the characteristics of human body pressure distribution, perspiration, heat dissipation, vibration environment, etc. The design of the foam pad fully considers the energy absorption characteristics under impact loads. The back pad is designed to be an "S" shape with two points of support at the shoulder and waist. The seat cushion is upturned to provide suitable support for the pilot's thighs. The angle between the seat surface and the horizontal plane is 7°, and the angle between the back of the back cushion and the seat surface of the seat cushion is 113°, ensuring the pilot's riding comfort.

[0038] like Figure 3As shown in Figure 6, there is at least one automatic variable load energy absorption device, which first measures the effective weight information of the pilot sitting on the seat through a weight sensor and sends data. After receiving the effective weight data, the electronic controller analyzes and calculates and sends the position information of the worm gear adjustment ring corresponding to the weight of the occupant to the servo motor. The servo motor receives the command and drives the worm gear to drive the worm gear adjustment ring to rotate. As the worm gear adjustment ring rotates, the steel ball moves either toward the center of the rolling tube or away from it, so that the protrusion of the steel ball in the spherical groove of the rolling tube can be adjusted. The size of the protrusion of the steel ball determines the size of the energy absorption work load. During the adjustment process, the rotary transformer monitors the angle position information in real time. When the specified position is reached, the servo motor stops working, and then the energy absorption work load is adjusted to the optimal working state corresponding to the effective weight of the pilot. Once an emergency landing accident occurs, the rolling tube and the roll tube in the energy absorption device undergo plastic deformation to absorb energy. At this time, the energy absorption device extends and ensures that the movable part of the human chair moves downward at 14.5g to prevent the pilot's lumbar spine from being overloaded and causing damage.

[0039] The automatic variable load energy absorption device includes a rolling tube 201, a turning tube 202, a support tube 203, a connecting sleeve 204, a steel ball 205, a single-ear joint 206, a support 207, a pull rod 208, a pull head 209, a bracket 210, a steel ball fixing outer cylinder 211, a joint 212, a double-ear joint 213, a worm gear adjustment ring 214, a worm 215, a limit screw 216, a servo motor 217, a weight sensor 218, a rotary transformer 219, a chassis 220, a transmission shaft 221, etc. Its specific structure is that the turning tube 202 is welded inside the supporting tube 203, the concave part of the pull head 209 is glued to the upper end of the turning tube 202, and the upper end of the supporting tube 2033 is welded inside the connecting sleeve 204. The upper end of the rolling tube 201 is welded to the outside of the connecting sleeve 204, and the lower end is welded to the supporting tube 203. The pull rod 208 passes through the support 207 and is connected to the pull head 209 by threads. The steel ball fixed outer cylinder 211 closes the rolling tube 201. Four limit screws 216 pass through the four strip grooves on the steel ball fixed outer cylinder 211 and are installed on the support tube 203 to ensure that the steel ball fixed outer cylinder 211 does not rotate and does not hinder the downward linear movement of the steel ball fixed outer cylinder 211. The weight sensor connector 218 passes through the hole of the steel ball fixed outer cylinder 211 and is threadedly connected to the pull rod 208. The worm gear adjustment ring 214 closes the four steel balls 205 in the four holes of the steel ball fixed outer cylinder 211, and the part of the steel ball 205 protruding from the inner surface of the steel ball fixed outer cylinder 211 is in the groove at the upper part of the rolling tube 201. The bracket 210 and the chassis 220 are respectively mounted on the steel ball fixed outer cylinder 211 by screws, and the worm gear adjustment ring 214 is restricted between the bracket 210 and the chassis 220, wherein the rotary transformer 219 and the worm gear adjustment ring 214 are connected together by interference fit. The servo motor 217 is mounted on the bracket 210, and the transmission shaft 221 passes through the hole on the ear piece of the bracket 210 and is connected to the worm 215 and the shaft on the servo motor 217. The upper end of the weight sensor 218 is connected to the weight sensor connector 212 by bolts. The worm 215 and the worm gear adjustment ring 214 form a set of worm and worm gear mechanism. The worm 215 is driven by the transmission shaft 221, thereby realizing the rotation of the worm gear adjustment ring 214. Figure 2 In the B-B view, the worm gear adjusting ring 214 surrounding the steel ball 205 has an arc-shaped groove inside corresponding to each steel ball 205. The rotation position of the worm gear adjusting ring 214 determines the position of the steel ball 205 in the groove. When the worm gear adjusting ring 214 rotates counterclockwise to a certain position, the steel ball 205 will be out of contact with the rolling tube 201, and when the worm gear adjusting ring 214 rotates clockwise to a certain position, the steel ball 205 will be in close contact with the rolling tube 201.

[0040] like Figure 7 As shown, in this embodiment, the rolling tube 201 is a thin-walled stainless steel tube with 4 depressions thereon.

[0041] like Figure 8 As shown, in this embodiment, the rolled tube 202 is a thin-walled stainless steel tube, which is formed by a mold, and a solution treatment is required during the forming process to eliminate the influence of cold work hardening.

[0042] like Fig. 9 As shown, in this embodiment, there are four arc-shaped grooves on the worm gear adjusting ring 214. It is necessary to apply lubricant on the inner surface of the arc-shaped groove.

[0043] like Fig.10 As shown, when the automatic variable load energy absorption device is working, the steel ball 205 and the steel ball fixing outer cylinder 211 move downward as a whole, and the rolling tube 202 turns over at the same time. Initially, static friction is generated between the steel ball 205 and the rolling tube 201. Later, the steel ball 205 moves slightly, and then the static friction is converted into rolling friction. The steel ball 205 squeezes the rolling tube 201, causing it to produce 4 uniform radial grooves. In this process, the rolling tube 201 and the rolling tube 202 undergo two different deformations at the same time: one is the axial deformation of the turning tube, which is turned inside out by inversion; the other is the radial deformation of the rolling tube 201 by the action of the steel ball 205. The device absorbs energy through these two plastic deformations.

[0044] like Fig.11 As shown, in this embodiment, the electronic controller has an energy absorption device control button for starting the automatic variable load energy absorption device. The display screen is used to display information such as the pilot's weight, angle, gear position, etc. The power light is used to display the power-on status. The status indicator light is used to indicate whether the automatic variable load energy absorption device is adjusted in place. The seat height adjustment button is used to control the seat surface height of the seat. Press the button forward, the seat height rises to the set highest position, and the button stops when it is released; press the button backward, the seat height drops to the set lowest position, and the button stops when it is released.

[0045] like Fig.12 As shown in the figure, the electronic controller hardware mainly includes power supply, force sensor signal conditioning circuit design, A / D acquisition circuit, main control MCU, motor controller and interface, etc. When the pilot sits on the seat and presses the control button of the energy absorption device, the force sensor first detects the weight signal, and the rotary transformer detects the angle position signal; then the controller analyzes and processes the angle position signal and weight signal, and issues an execution command to drive the servo motor; after the servo motor is executed, the controller automatically determines whether the servo motor rotates to the specified angle (position) according to the original setting program, and issues an alarm signal if the specified angle (position) cannot be detected.

[0046] like Fig.13As shown in Figure 16, the frame includes a main chair leg 301, a movable chair leg 302, a bushing 303, an upper crossbar 304, a lower crossbar 305, a connecting joint 306, a push rod connecting joint 307, an upper sliding sleeve assembly 308, a lower sliding sleeve assembly 309, a front and rear sliding block assembly 310, a long gasket 311, etc. The frame is the main load-bearing member of the seat system, wherein the main chair leg 301, the movable chair leg 302, the upper crossbar 304, and the lower crossbar 305 form a stable rectangular structural frame. The upper sliding sleeve assembly 308 includes a gasket 312, a bearing sleeve 313, a bearing retaining ring 314, a bearing 315, an upper slider 316, etc. The bearing 315 is installed inside the bearing sleeve 313 and fixed with a bearing retaining ring 314. The assembly formed by them is connected to the upper slider 316 through bolts and nuts. The gasket 312 is installed at the bottom of the cavity of the upper slider 316. The above parts form an upper sleeve assembly 308, which is mounted on the movable chair leg 302, wherein the bearing sleeve 313 can roll freely on the rear surface of the movable chair leg 302, and the gasket 312 can slide freely on the front surface of the movable chair leg 302. Similar to the upper sleeve assembly 308, the assembly formed by the bearing sleeve 313, the bearing retaining ring 314, and the bearing 315 in the lower sleeve assembly 309 is installed at the bottom of the cavity of the lower slider 317, and can roll freely on the front surface of the movable chair leg 302. The limit plate 318 is installed on both sides of the lower slider 317 by bolts and nuts, and is respectively clamped on the edge of the weight reduction groove of the movable chair leg 302, so that it can slide up and down along this edge. The upper sleeve assembly 308 and the lower sleeve assembly 309 are both installed in pairs on the back of the armored chair basin. The main chair legs 301 and the movable chair legs 302 are both provided with relatively long waist-shaped grooves. After being connected to each other through bushings 303, the movable chair legs 302 can be raised and lowered and slid on the main chair legs 301, and the seat height can be adjusted by the action of an electric push rod connected between the upper cross bar and the lower cross bar.

[0047] like Fig.17As shown in FIG. 18, the bulletproof armored chair basin includes a left armor 401, a right armor 402, an armored chair basin 403, a left bow 404, a right bow 405, etc. The left armor 401 and the right armor 402 adopt the same bulletproof structure as the bottom armor of the armored chair basin 403, and the side armor bearing layer is connected and fastened to the left bow 404 and the right bow 405 by bolts and self-locking nuts. After the side armor is installed, it can ensure the accessibility of the 5th to 95th percentile pilots to operate the helicopter without obstructing their vision. The left and right armors and the armored chair basin 403 are connected in a quick-release manner. It is only necessary to remove a bolt and nut and other fasteners connecting the left and right armors to the armored chair basin 403, and lift the left and right armors upwards respectively, and the left and right armors can be removed. The back of the armored chair basin 403 is prefabricated with inertia reel, upper sliding sleeve assembly, upper sliding sleeve assembly and other installation holes, the left and right sides and the bottom are prefabricated with waist belt and crotch belt installation holes, the bottom is prefabricated with front and rear sliding adjustment handle installation holes, and the left oblique front side is prefabricated with seat belt adjustment handle installation holes. The function of the bulletproof ceramic panel is to crush the warhead so that the highly concentrated energy of the warhead is dispersed. The bulletproof ceramic panel is formed by efficient and rapid sintering process and electric spark machining process. The ultra-high molecular weight polyethylene plate can absorb the remaining kinetic energy of the warhead through its own large deformation.

[0048] like Fig.19 As shown, in this embodiment, the forward and backward sliding adjustment handle includes a mounting seat 501, a handle rotating connecting rod 502, a steel bushing 503, a torsion spring 504, a handle rod 505, a handle sleeve 506, an adjustment screw 507, a steel cable assembly 508, etc. The handle sleeve 506 is an injection molded part, which is sleeved on the handle rod 505, and the handle rod 505 is riveted on the handle rotating connecting rod 502. The mounting seat 501, the handle rotating connecting rod 502, the steel bushing 503, and the torsion spring 504 are connected by bolts and nuts. The steel cable assembly 508 is connected to the rear end of the handle rotating connecting rod 502 by bolts and nuts. The adjustment screw 507 is installed on the handle rotating connecting rod 502 for adjusting the installation angle of the handle. The mounting seat 501 is installed at the bottom of the armored seat basin by screws. When the pilot pulls the handle upward, the locking mechanism is unlocked by pulling the steel cable assembly 508. After the handle is released, the handle can return to the initial position under the action of the torsion spring 504.

[0049] like Fig. 20As shown, in this embodiment, the front-to-back sliding adjustment locking mechanism includes a front-to-back sliding locking pin 601, a sleeve 602, a spring 603, a thin nut 604, and a steel cable assembly 508. The mechanism is installed on the main chair leg. When the pilot adjusts the seat front-to-back, he pulls the handle upward by hand to pull the steel cable assembly 508, so that the locking pin 601 of the locking control mechanism is pulled out from the locking hole of the guide rail, and the pilot moves the seat forward or backward. When the seat moves to a suitable position, the pilot releases the handle, and the locking pin 601 is inserted into the locking hole on the guide rail under the action of the spring 603 in the locking control mechanism, so that the seat is locked in a suitable position.

[0050] Working principle of this utility model:

[0051] When the seat is in normal use, the driver can fasten the seat belt to protect safety, and the seat height can be adjusted by adjusting the lifting and sliding components to improve riding comfort and meet the different work needs of the driver; when the helicopter makes an emergency landing, the energy absorber works to absorb part of the crash energy and effectively protect the personal safety of the driver and the shooter; when the helicopter is attacked, the seat armor can be bulletproof to protect the lives of the occupants. The bulletproof armored seat basin and side armor both adopt a bulletproof structure in which a bulletproof ceramic panel is pasted on the outside of the carbon fiber load-bearing member and an ultra-high molecular weight polyethylene plate is pasted on the inside. The crack-stop cloth is pasted on the outside of the bulletproof ceramic panel, and all armor edges are covered with edge strips to protect the pilot from being cut by the ceramic edges.

[0052] The above technical solutions are only preferred embodiments of the present application, and certainly cannot be used to limit the scope of rights of the present application. Therefore, equivalent changes made within the scope of the patent of the present application still fall within the protection scope of the present application.

Claims

1. A helicopter seat system capable of automatically changing load and absorbing energy, comprising a frame (1), a bulletproof armored seat pan (2), an electronic controller (8), an adjustment locking mechanism (9), a guide rail (10), an electric push rod (11) and an automatic variable load and energy absorbing device (12), wherein the guide rail (10) is fixed on the cabin floor, the frame (1) is mounted on the guide rail (10), the upper surface of the guide rail (10) is provided with a circular hole, the seat system can be manipulated to slide forward and backward, and the adjustment locking mechanism (9) can slide on the guide rail (10) and lock at the circular hole thereof, It is characterized in that The bulletproof armored chair basin (2) is installed on the movable chair legs of the frame (1) and fixed by bolts. The upper end of the automatic variable load energy absorption device (12) is connected to the energy absorber connection joint of the frame (1) by bolts, and the lower end is connected to the lower joint (13) installed on the bulletproof armored chair basin (2) by bolts. The electronic controller (8) is installed on the bulletproof armored chair basin (2), which is connected to the automatic variable load energy absorption device (12) through a cable and realizes control. The electric push rod (11) is installed between the upper cross bar and the lower cross bar of the frame (1). The adjustment locking mechanism (9) is provided with a handle and a locking mechanism for making it slide forward and backward. The forward and backward sliding handle is installed below the bulletproof armored chair basin (2), and the locking mechanism is installed at the bottom of the main chair leg of the frame (1); the seat system includes at least one electric push rod for guiding at least one armored chair basin to move up and down to realize seat height adjustment. The electric push rod is a straight rod type, which can be extended and retracted to realize stepless adjustment, and the stroke can be self-locking.

2. A helicopter seat system capable of automatically changing load and absorbing energy according to claim 1, It is characterized in that The seat system also includes a five-point safety belt (3), which includes an inertia reel and a control handle, wherein the inertia reel is installed on the back of the bulletproof armored seat basin (2), and the control handle is installed on the left front side of the bulletproof armored seat basin (2).

3. A helicopter seat system capable of automatically changing load and absorbing energy according to claim 1, It is characterized in that The seat system also includes a headrest (4), a back cushion (5), an electric push rod lumbar cushion (6) and a seat cushion (7). The headrest (4), the back cushion (5), the electric push rod lumbar cushion (6) and the seat cushion (7) are arranged and fixed at corresponding positions when the occupant is seated. The seat cushion (7) is a foamed part made of a double-layer material of polyurethane foam and flame-retardant low-resilience polyethylene foam. The headrest (4), the back cushion (5) and the electric push rod lumbar cushion (6) are foamed parts made of polyurethane foam material. The back cushion (5) is designed to be an "S" shape with shoulder and waist support at two points. The seat cushion (7) is tilted upward to support the pilot's thighs. The angle between the seat surface and the horizontal plane is 7 degrees. The angle between the backrest surface of the back cushion (5) and the seat cushion surface is 113 degrees, so as to ensure the pilot's riding comfort.

4. A helicopter seat system capable of automatically changing load and absorbing energy according to claim 1, It is characterized in that The automatic variable load energy absorption device (12) comprises a rolling tube (201), a flip tube (202), a support tube (203), a connecting sleeve (204), a single-ear joint (206), a support member (207), a pull rod (208), a pull head (209), a steel ball fixing outer cylinder (211), a double-ear joint (213), a limit screw (216), a rotary transformer (219), a chassis (220), the flip tube (202) is welded inside the support tube (203), a recessed portion of the pull head (209) is coated with glue and glued to the upper end of the flip tube (202), the upper end of the support tube (203) is welded inside the connecting sleeve (204), the upper end of the rolling tube (201) is welded to the connecting sleeve ( The outer part of the steel ball fixing outer cylinder (204) is welded to the support tube (203) at the lower end, the pull rod (208) passes through the support member (207) and is connected to the pull head (209) by threads, and the steel ball fixing outer cylinder (211) closes the rolling tube (201); four limit screws (216) pass through the four strip grooves on the steel ball fixing outer cylinder (211) and are installed on the support tube (203) to ensure that the steel ball fixing outer cylinder (211) will not rotate and hinder the steel ball fixing outer cylinder (211) from moving linearly downward, and the worm gear adjustment ring (214) closes the four steel balls (205) in the groove on the upper part of the rolling tube (201) where the part of the steel ball fixing outer cylinder (211) protruding from the inner surface of the steel ball fixing outer cylinder (211); The bracket (210) and the chassis (220) are respectively mounted on the steel ball fixed outer cylinder (211) by means of screws, and the worm gear adjustment ring (214) is restricted between the bracket (210) and the chassis (220), wherein the rotary transformer (219) and the worm gear adjustment ring (214) are connected together by means of interference fit.

5. A helicopter seat system capable of automatically changing load and absorbing energy according to claim 4, It is characterized in that The automatic variable load energy absorption device (12) further comprises a steel ball (205), a bracket (210), a joint (212), a worm gear adjustment ring (214), a worm (215), a servo motor (217), a weight sensor (218), and a transmission shaft (221); the servo motor (217) is mounted on the bracket (210); the transmission shaft (221) passes through a hole on an ear piece of the bracket (210) and is connected to the shaft on the worm (215) and the servo motor (217); the upper end of the weight sensor (218) The weight sensor connector (212) is connected with the weight sensor connector (218) through a hole of the steel ball fixing outer cylinder (211) and is threadedly connected with the pull rod (208); the worm gear adjustment ring (214) surrounding the steel ball (205) has an arc-shaped groove inside corresponding to each steel ball (205); the worm (215) and the worm gear adjustment ring (214) form a set of worm gear mechanism; the worm (215) is driven by the transmission shaft (221), thereby realizing the rotation of the worm gear adjustment ring (214).

6. A helicopter seat system capable of automatically changing load and absorbing energy according to claim 1, It is characterized in that The bulletproof armored chair basin includes a left side armor, a right side armor, an armored chair basin, a left bow-shaped piece, a right bow-shaped piece and an armored load-bearing piece. The armored load-bearing piece is fastened together with the left bow-shaped piece and the right bow-shaped piece by bolts and self-locking nuts respectively. The left side armor, the right side armor and the armored chair basin are connected in a quick-release manner.

7. A helicopter seat system capable of automatically changing load and absorbing energy according to claim 6, It is characterized in that The bulletproof armored chair basin adopts a bulletproof structure in which a bulletproof ceramic panel is pasted on the outside of a carbon fiber load-bearing member and an ultra-high molecular weight polyethylene plate is pasted on the inside. Crack-stop cloth is wrapped and pasted on the outside of the bulletproof ceramic panel, and all armor edges are covered with edge strips to protect the pilot from being cut by the ceramic edges.

8. A helicopter seat system capable of automatically changing load and absorbing energy according to claim 1, It is characterized in that The frame includes main chair legs, movable chair legs, bushings, upper cross bars, lower cross bars, energy absorber connecting joints, push rod connecting joints, upper sliding sleeve assemblies, lower sliding sleeve assemblies, front and rear sliding block assemblies and long gaskets. Solid dry film lubricant is applied to the relative movement position of the frame; the guide rail is connected to the floor, and the guide rail is in the form of an I-beam with round holes on the upper surface; a long polytetrafluoroethylene gasket is provided at the contact position between the front and rear sliding block assemblies and the upper surface of the guide rail, and a rolling bearing is provided at the contact position between the lower sliding sleeve assembly and the surface of the movable chair leg. The spacing between the main chair legs is adapted and adjusted according to the floor interface requirements of different models of aircraft.

9. A helicopter seat system capable of automatically changing load and absorbing energy according to claim 1, It is characterized in that The frame includes a main chair leg, a movable chair leg, a bushing, an upper cross bar, a lower cross bar, a connecting joint, a push rod connecting joint, an upper sliding sleeve assembly, a lower sliding sleeve assembly, a front and rear sliding block assembly and a long gasket. The main chair leg, the movable chair leg, the upper cross bar and the lower cross bar are connected together to form a stable rectangular structural frame. The upper sliding sleeve assembly includes a gasket, a bearing hoop, a bearing retaining ring, a bearing and an upper slider. The bearing is installed inside the bearing hoop and fixed with a bearing retaining ring. It is connected to the upper slider by bolts and nuts. The gasket is installed at the bottom of the cavity of the upper slider. The upper sliding sleeve assembly is mounted on the movable chair leg. The limit plates are installed on both sides of the lower sliding block by bolts and nuts, and are respectively clamped on the edge of the movable chair leg weight reduction groove, so that they can slide up and down along this edge. The upper sliding sleeve assembly and the lower sliding sleeve assembly are installed in pairs on the back of the armored chair basin. The main chair legs and movable chair legs have long waist-shaped grooves. After being connected to each other by bushings, the movable chair legs can be raised and lowered and slid on the main chair legs, and the seat height adjustment is achieved by the action of an electric push rod connected between the upper cross bar and the lower cross bar.

10. A helicopter seat system capable of automatically changing load and absorbing energy according to claim 1, It is characterized in that The helicopter seat system also includes a forward and backward sliding adjustment handle, which includes a mounting seat, a handle rotating connecting rod, a steel bushing, a torsion spring, a handle rod, a handle cover, an adjusting screw and a steel cable assembly. The handle cover is an injection molded part, which is sleeved on the handle rod. The handle rod is riveted to the handle rotating connecting rod. The mounting seat, the handle rotating connecting rod, the steel bushing and the torsion spring are connected by bolts and nuts. The steel cable assembly is connected to the rear end of the handle rotating connecting rod by bolts and nuts. The adjusting screw is installed on the handle rotating connecting rod. The mounting seat is installed on the bottom of the armored seat basin by screws. When the pilot pulls the handle upward, the locking mechanism is unlocked by pulling the steel cable assembly. After the handle is released, the handle can return to its initial position under the action of the torsion spring.

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